A thrust augmenting combustion chamber with adaptive adjustment of strut front edge and stabilizer and a control method thereof

Abstract

This application relates to an afterburner with adaptive adjustment of the support plate leading edge and stabilizer, and its control method. The afterburner includes a casing, a central guide vane, an outer ring, and multiple support plates distributed circumferentially between the central guide vane and the outer ring. Each support plate includes a leading edge section and a main body section distributed sequentially along the axial direction. The main body section connects the outer ring and the central guide vane. The leading edge section is rotatably connected to the main body section. The afterburner also includes a drive mechanism connected to the leading edge section. The drive mechanism drives the leading edge section to rotate relative to the main body section to adjust the angle of the leading edge section relative to the airflow direction. This allows the leading edge section of the support plate to adapt to changes in the airflow direction, reducing the probability of the leading edge section generating a non-zero angle of attack. This reduces the likelihood of airflow separation, flow field distortion, and oscillation within the afterburner, maximizing the reduction of flow resistance loss and improving thrust and combustion stability.

Description

Technical Field

[0001] This application relates to the field of aero-engine technology, and in particular to an afterburner with adaptive adjustment of the leading edge of the support plate and the stabilizer, and a control method thereof. Background Technology

[0002] The afterburner is a key component of military aircraft engines. It works by injecting fuel into the exhaust gas from the engine. Due to the high temperature of the exhaust, the fuel burns in real time, expanding and generating additional thrust. Its purpose is to support aircraft in performing short takeoff, aerial maneuvers, and supersonic cruise by providing a significant, instantaneous increase in thrust. To achieve these goals, the afterburner must possess low flow drag loss and highly reliable flame stability; these are the core aspects of its technological development.

[0003] In related technologies, the support plate of the afterburner adopts a fixed geometric configuration. Within the actual operating envelope of the engine, due to factors such as changes in core engine speed, changes in flight attitude, or inlet distortion, the direction of airflow entering the afterburner (airflow angle of attack) will change significantly. This makes it easy for the leading edge of the support plate to generate a non-zero angle of attack, resulting in the risk of airflow separation, flow field distortion, and oscillation within the afterburner. This leads to significant flow resistance damage to the engine, reducing engine thrust and combustion stability. Summary of the Invention

[0004] Therefore, it is necessary to provide an afterburner with adaptive adjustment of the leading edge of the support plate and the stabilizer, and its control method, to address the problem that the leading edge of the afterburner is prone to generating a non-zero angle of attack.

[0005] An afterburner with adaptive adjustment of the leading edge of the support plate and the stabilizer includes a casing, a central guide, an outer ring, and a plurality of support plates distributed circumferentially and located between the central guide and the outer ring;

[0006] The support plate includes a leading edge section and a main body section distributed sequentially along the axial direction; the main body section connects the outer ring and the central guide member; the leading edge section is rotatably connected to the main body section.

[0007] The afterburner also includes a drive mechanism connected to the leading edge section. The drive mechanism is used to drive the leading edge section to rotate relative to the main body section in order to adjust the angle of the leading edge section relative to the airflow direction.

[0008] In one embodiment, the drive mechanism is located between the outer ring and the housing, and the drive mechanism includes:

[0009] A first transmission member is connected to the leading edge segment;

[0010] A driving member is disposed on the outer ring or the housing; the driving member is connected to the first transmission member, and the driving member is used to drive the first transmission member to swing, so as to drive the leading edge segment to rotate relative to the main body segment.

[0011] In one embodiment, the drive mechanism further includes a second transmission member and a plurality of third transmission members;

[0012] The second transmission member is disposed between the outer ring and the housing, and the second transmission member is constructed as a ring structure; the second transmission member is capable of rotating about the axial direction of the outer ring;

[0013] The first transmission member is connected to the leading edge segment of one of the support plates; the end of the first transmission member away from the drive member is connected to the second transmission member via a spherical joint.

[0014] The plurality of third transmission components are connected to the leading edge segments of the remaining support plates, and the plurality of third transmission components are all connected to the second transmission component through a spherical pair.

[0015] In one embodiment, the afterburner further includes a connector connected to the leading edge segment, and the first transmission member or the third transmission member is connected to the connector.

[0016] In one embodiment, the connector is inserted through the leading edge segment along the direction from the outer ring toward the central guide member;

[0017] The end of the connector near the central guide is rotatably connected to the central guide; the end of the connector near the outer ring passes through the outer ring and is connected to the first transmission member or the third transmission member.

[0018] In one embodiment, the main body segment includes a middle segment and a tail segment. The middle segment is rotatably connected to the leading edge segment, and the side of the middle segment away from the leading edge segment is connected to the tail segment. A fuel passage is provided in the tail segment, a fuel nozzle is provided on the side wall of the tail segment, and a flame stabilizing structure is provided on the side of the tail segment away from the leading edge segment.

[0019] In one embodiment, the afterburner further includes a controller and a position sensor, the controller being connected to the position sensor and the drive mechanism, the position sensor being used to monitor the rotation angle of the leading edge segment; the controller being used to control the operation of the drive mechanism based on the rotation angle information monitored by the position sensor.

[0020] A control method for an afterburner with adaptive adjustment of the leading edge of the support plate and the stabilizer, the method comprising:

[0021] Obtain the airflow deflection angle β of the airflow entering the afterburner;

[0022] Based on the airflow deflection angle β and the mounting angle θ of the support plate fixed The target rotation angle δ of the leading edge segment is calculated.

[0023] The leading edge segment is controlled to rotate through the target rotation angle δ so that the tangent direction of the mid-arc line of the leading edge segment is consistent with the airflow direction.

[0024] In one embodiment, the step of obtaining the airflow deflection angle β of the airflow entering the afterburner includes:

[0025] Obtain the flow field parameters of the airflow entering the afterburner, or obtain the compressor speed and turbine pressure ratio;

[0026] The obtained flow field parameters, or the compressor speed and turbine pressure ratio, are input into the preset calibrated flow field model to calculate the airflow deflection angle β.

[0027] In one embodiment, the formula for calculating the target rotation angle δ of the leading edge segment is:

[0028] δ=β-θ fixed .

[0029] The aforementioned adaptive adjustment of the support plate leading edge and stabilizer in the afterburner and its control method allows for convenient control of the leading edge section relative to the main body section by rotatably connecting the leading edge section of the support plate to the main body section and connecting the drive mechanism to the leading edge section. This adjusts the angle of the leading edge section relative to the airflow direction, ensuring that the tangent direction of the mid-arc of the leading edge section aligns with the airflow direction. In other words, the leading edge section of the support plate can adapt to changes in airflow direction, reducing the probability of the leading edge section of the support plate generating a non-zero angle of attack. This reduces the likelihood of airflow separation, flow field distortion, and oscillation risks within the afterburner, maximizing the reduction of flow resistance loss and improving thrust and combustion stability. Attached Figure Description

[0030] Figure 1 This is a cross-sectional view of the overall structure of the afterburner with adaptive adjustment of the leading edge of the support plate and the stabilizer in some embodiments of this application.

[0031] Figure 2 This is a partial structural schematic diagram of the drive mechanism in some embodiments of this application.

[0032] Figure 3 This is a schematic diagram of the support plate structure in some embodiments of this application.

[0033] Figure 4 This is a schematic diagram illustrating the adjustment principle of the leading edge section of the support plate under the first airflow angle of attack in some embodiments of this application.

[0034] Figure 5 This is a schematic diagram illustrating the adjustment principle of the leading edge section of the support plate under the second airflow angle of attack in some embodiments of this application.

[0035] Figure 6 This is a flowchart of a control method for an adaptively adjusted afterburner chamber using the leading edge of the support plate and the stabilizer in some embodiments of this application.

[0036] Explanation of reference numerals in the attached figures:

[0037] 10. Afterburner; 11. Casing; 12. Central guide vane; 121. Inner ring; 122. Central cone; 13. Outer ring; 14. Support plate; 141. Leading edge section; 142. Main body section; 142a. Middle section; 142b. Tail section; 142b1. Flame stabilization structure; 15. Drive mechanism; 151. First transmission component; 152. Drive component; 153. Second transmission component; 154. Third transmission component; 16. Connecting component. Detailed Implementation

[0038] To make the above-mentioned objectives, features, and advantages of this application more apparent and understandable, the specific embodiments of this application are described in detail below with reference to the accompanying drawings. Many specific details are set forth in the following description to provide a thorough understanding of this application. However, this application can be implemented in many other ways different from those described herein, and those skilled in the art can make similar modifications without departing from the spirit of this application. Therefore, this application is not limited to the specific embodiments disclosed below.

[0039] In the description of this application, it should be understood that if terms such as "center", "longitudinal", "lateral", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise", "axial", "radial", "circumferential" appear, these terms indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings, and are only for the convenience of describing this application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of this application.

[0040] Furthermore, where the terms "first" and "second" appear, these terms are for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of technical features indicated. Thus, a feature defined with "first" or "second" may explicitly or implicitly include at least one of that feature. In the description of this application, where the term "multiple" appears, "multiple" means at least two, such as two, three, etc., unless otherwise explicitly specified.

[0041] In this application, unless otherwise expressly specified and limited, the terms "installation," "connection," "joining," and "fixing," etc., should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral part; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; they can refer to the internal communication of two components or the interaction between two components, unless otherwise expressly limited. Those skilled in the art can understand the specific meaning of the above terms in this application based on the specific circumstances.

[0042] In this application, unless otherwise expressly specified and limited, the use of descriptions such as "above" or "below" the second feature indicates that the first and second features are in direct contact or indirect contact via an intermediate medium. Furthermore, "above," "on top of," and "over" the second feature can mean that the first feature is directly above or diagonally above the second feature, or simply that the first feature is at a higher horizontal level than the second feature. Similarly, "below," "below," and "under" the second feature can mean that the first feature is directly below or diagonally below the second feature, or simply that the first feature is at a lower horizontal level than the second feature.

[0043] It should be noted that if an element is referred to as being "fixed to" or "set on" another element, it can be directly on the other element or there may be an intervening element. If an element is considered to be "connected to" another element, it can be directly connected to the other element or there may be an intervening element. If so, the terms "vertical," "horizontal," "upper," "lower," "left," "right," and similar expressions used in this application are for illustrative purposes only and do not represent the only possible implementation.

[0044] In related technologies, the support plate of the afterburner adopts a fixed geometric configuration. Within the actual operating envelope of the engine, due to factors such as changes in core engine speed, flight attitude, or inlet distortion, the direction of airflow entering the afterburner (airflow angle of attack) will change significantly, making it easy for the leading edge of the support plate to generate a non-zero angle of attack. This leads to risks of airflow separation, flow field distortion, and oscillation within the afterburner. Airflow separation includes premature separation of airflow on the support plate surface, forming a separation zone, generating significant drag and wake loss, and reducing the total pressure recovery system of the afterburner. Flow field distortion includes the separation zone interfering with subsequent fuel atomization and flame propagation, potentially leading to localized fuel richness or leanness, affecting combustion efficiency. Oscillation risks include airflow shedding at high angles of attack potentially inducing oscillating combustion, threatening structural safety, causing significant flow resistance damage to the engine, and reducing engine thrust and combustion stability.

[0045] Based on the above-mentioned technical problems, this application provides an afterburner and its control method that can adaptively adjust the leading edge of the support plate and the stabilizer to adapt to changes in airflow direction, so as to reduce the probability of airflow separation, flow field distortion and oscillation risk in the afterburner, maximize the reduction of flow resistance loss and improve thrust and combustion stability.

[0046] Figure 1 This paper shows a cross-sectional view of the overall structure of the afterburner with adaptive adjustment of the support plate leading edge and stabilizer in one embodiment of the present application. Figure 3 A schematic diagram of the support plate in some embodiments of this application is shown.

[0047] Firstly, see Figure 1 and Figure 3 As shown, an embodiment of this application provides an afterburner 10 with adaptive adjustment of the leading edge of the support plate and the stabilizer, including a casing 11, a central guide 12, an outer ring 13, and a plurality of support plates 14 distributed circumferentially and located between the central guide 12 and the outer ring 13; the support plate 14 includes a leading edge section 141 and a main body section 142 distributed sequentially along the axial direction, the main body section 142 connecting the outer ring 13 and the central guide 12; the leading edge section 141 is rotatably connected to the main body section 142; the afterburner 10 also includes a drive mechanism 15, the drive mechanism 15 is connected to the leading edge section 141, and the drive mechanism 15 is used to drive the leading edge section 141 to rotate relative to the main body section 142 to adjust the angle of the leading edge section 141 relative to the airflow direction.

[0048] The afterburner 10 can be used in an aero-engine. The afterburner 10 can be arranged in a flow channel between the turbine outlet (not shown) and the tail nozzle (not shown). The afterburner 10 includes an inlet (not shown) and an outlet (not shown), with the inlet communicating with the turbine outlet and the outlet communicating with the tail nozzle. The leading edge section 141 is located near the inlet and is used to straighten the airflow. The main body section 142 is fixedly connected between the outer ring 13 and the central guide member 12, primarily providing support and bearing structural loads. The central guide member 12 includes an inner ring 121 and a central cone 122 connected sequentially along the axial direction. The central cone 122 is located on the side of the inner ring 121 away from the leading edge section 141. The main body section 142 is fixedly connected between the outer ring 13 and the inner ring 121.

[0049] The leading edge segment 141 can be connected to the main body segment 142 via a hinge, but it is not limited to this; other structures can also be used to achieve a rotatable connection between the leading edge segment 141 and the main body segment 142. The mating surface between the leading edge segment 141 and the main body segment 142 is an arc transition, ensuring the continuity of the aerodynamic shape of the support plate 14 during the rotation of the leading edge segment 141 and reducing interference from the gap flow.

[0050] It should be noted that the circumferential direction can be the circumferential direction of the outer ring 13; the axial direction can be the axial direction of the outer ring 13.

[0051] The leading edge segment 141 is rotatably connected to the main body segment 142, and the drive mechanism 15 is connected to the leading edge segment 141. The drive mechanism 15 is used to drive the leading edge segment 141 to rotate relative to the main body segment 142, so as to adjust the angle of the leading edge segment 141 relative to the airflow direction, so that the tangent direction of the mid-arc line of the leading edge segment 141 is consistent with the airflow direction. In other words, it enables the leading edge segment 141 of the support plate 14 to adapt to the change of airflow direction, reducing the probability of the leading edge segment 141 of the support plate 14 generating a non-zero angle of attack. Thus, on the one hand, it can reduce the probability of airflow separation in the leading edge segment 141, significantly reduce the total pressure loss, and maximize the reduction of flow resistance loss; on the other hand, it can reduce the wake and vortex generated by separation, making the flow field entering the combustion zone more uniform, which is conducive to fuel atomization and flame propagation, improves combustion efficiency, and helps to increase thrust; in addition, it can effectively suppress airflow shedding and oscillation at large angles of attack, reduce the risk of oscillating combustion in the afterburner 10, improve combustion stability, and broaden the stable operating range.

[0052] In summary, the afterburner 10 with adaptive adjustment of the support plate leading edge and stabilizer provided in this application embodiment allows for convenient control of the rotation of the leading edge section 141 relative to the main body section 142 by rotatably connecting the supporting plate 14 of the afterburner 10 to the main body section 142, and connecting the drive mechanism 15 to the leading edge section 141. This adjusts the angle of the leading edge section 141 relative to the airflow direction, ensuring that the tangent direction of the mid-arc line of the leading edge section 141 is consistent with the airflow direction. In other words, the leading edge section 141 of the support plate 14 can adapt to changes in the airflow direction, reducing the probability of the leading edge section 141 of the support plate 14 generating a non-zero angle of attack. This reduces the probability of airflow separation, flow field distortion, and oscillation risks within the afterburner 10, maximizing the reduction of flow resistance loss and improving thrust and combustion stability.

[0053] Figure 2 A partial structural schematic diagram of the drive mechanism in some embodiments of this application is shown.

[0054] In one embodiment, combined with Figure 1 and Figure 2 As shown, the drive mechanism 15 is located between the outer ring 13 and the housing 11. The drive mechanism 15 includes a first transmission member 151 and a drive member 152. The first transmission member 151 is connected to the leading edge section 141. The drive member 152 is disposed on the outer ring 13 or the housing 11. The drive member 152 is connected to the first transmission member 151. The drive member 152 is used to drive the first transmission member 151 to swing, so as to drive the leading edge section 141 to rotate relative to the main body section 142.

[0055] From the perspective shown in the attached figure, the driving member 152 is disposed on the outer ring 13. The driving member 152 is hinged to the first transmission member 151. The first transmission member 151 is connected to the leading edge segment 141 through the connecting member 16. The connecting member 16 is connected to the leading edge segment 141. The first transmission member 151 is connected to the connecting member 16. The driving member 152 is used to drive the first transmission member 151 to swing, thereby causing the connecting member 16 and the leading edge segment 141 to swing, thereby causing the leading edge segment 141 to rotate relative to the main body segment 142.

[0056] Therefore, by placing the drive mechanism 15 between the outer ring 13 and the casing 11, the high-temperature gas flow channel inside the afterburner 10 can be avoided, preventing the high-temperature gas from causing erosion or interference to the drive mechanism 15, thus improving the reliability and service life of the drive mechanism 15. By placing the drive component 152 on the outer ring 13 or the casing 11, it is fixed firmly and easy to install and maintain. The drive component 152 is connected to the leading edge section 141 through the first transmission component 151. The drive component 152 drives the first transmission component 151 to swing, thereby driving the leading edge section 141 to rotate. The transmission is precise and the response is rapid. The angle of the leading edge section 141 can be smoothly adjusted, allowing the leading edge section 141 of the support plate 14 to adapt to changes in airflow direction and reducing the probability of the leading edge section 141 of the support plate 14 generating a non-zero angle of attack. In addition, the drive mechanism 15 does not occupy the flow channel space and does not interfere with the internal airflow, further ensuring the stability of the flow field. Combined with the angle adjustment of the leading edge section 141, it effectively reduces flow resistance and oscillation risk, improving the overall performance of the afterburner 10.

[0057] It should be noted that in this embodiment, there can be multiple drive mechanisms 15, and multiple drive mechanisms 15 are connected one-to-one with multiple support plates 14. Multiple drive mechanisms 15 can drive the leading edge sections 141 of multiple support plates 14 to rotate synchronously. In this way, the angle of the leading edge sections 141 of all support plates 14 relative to the airflow direction can be easily adjusted, so that the leading edge sections 141 of all support plates 14 can adapt to the change of airflow direction, reducing the probability of the leading edge sections 141 of all support plates 14 generating a non-zero angle of attack. This can further reduce the probability of airflow separation, flow field distortion and oscillation risk in the afterburner 10, maximize the reduction of flow resistance loss, and further improve thrust and combustion stability.

[0058] Figure 4 This invention illustrates a schematic diagram of the adjustment principle of the leading edge section of the support plate under the first airflow angle of attack in some embodiments of this application. Figure 5 A schematic diagram illustrating the adjustment principle of the leading edge section of the support plate under the second airflow angle of attack in some embodiments of this application is shown.

[0059] In one embodiment, see [reference] Figure 2As shown, the drive mechanism 15 also includes a second transmission member 153 and a plurality of third transmission members 154; the second transmission member 153 is disposed between the outer ring 13 and the housing 11, and the second transmission member 153 is constructed as a ring structure; the second transmission member 153 is rotatable about the axial direction of the outer ring 13; the first transmission member 151 is connected to the leading edge section 141 of a support plate 14; the end of the first transmission member 151 away from the drive member 152 is connected to the second transmission member 153 through a spherical joint; the plurality of third transmission members 154 are connected to the leading edge sections 141 of the remaining support plates 14, and the plurality of third transmission members 154 are all connected to the second transmission member 153 through a spherical joint.

[0060] From the perspective shown in the attached figure, the leading edge segment 141 of each plate 14 is connected to the connector 16, the first transmission member 151 is connected to the connector 16 on the corresponding leading edge segment 141, and the third transmission member 154 is connected to the connector 16 on the corresponding leading edge segment 141; the first transmission member 151 and the plurality of third transmission members 154 are all connected to the second transmission member 153 through ball joints.

[0061] See Figure 4 and Figure 5 It can be seen that under different airflow directions (airflow angle of attack), when the first transmission component 151 is driven to swing by the driving component 152, the first transmission component 151 drives the corresponding leading edge segment 141 to rotate, while driving the second transmission component 153 to rotate circumferentially. The second transmission component 153 then drives all the third transmission components 154 to swing, thereby driving all the leading edge segments 141 to rotate synchronously. In this way, the tangent direction of the middle arc of the leading edge segment 141 of all the support plates 14 is consistent with the airflow direction.

[0062] It should be noted that, Figure 4 and Figure 5 The arrows in the text indicate the direction of airflow.

[0063] In this embodiment, the first transmission member 151 is driven to swing by the driving member 152. The first transmission member 151 drives the corresponding leading edge segment 141 to rotate, while simultaneously driving the second transmission member 153 to rotate circumferentially. The second transmission member 153 then drives all the third transmission members 154 to swing, thereby driving all the leading edge segments 141 to rotate synchronously. In this way, the angle of the leading edge segment 141 of all the support plates 14 relative to the airflow direction can be easily adjusted, so that the leading edge segment 141 of all the support plates 14 can adapt to changes in the airflow direction, reducing the probability of the leading edge segment 141 of all the support plates 14 generating a non-zero angle of attack. This further reduces the probability of airflow separation, flow field distortion and oscillation risks in the afterburner 10, maximizes the reduction of flow resistance loss, and further improves thrust and combustion stability.

[0064] It should be noted that the drive component 152 can be a high-temperature resistant servo motor, a hydraulic actuator, a pneumatic actuator, etc. Both the first transmission component 151 and the third transmission component 154 can be rocker arms.

[0065] In one embodiment, combined with Figure 2 and Figure 3 As shown, the afterburner 10 also includes a connector 16, which is connected to the leading edge section 141, and the first transmission member 151 or the third transmission member 154 is connected to the connector 16.

[0066] Thus, by setting the connector 16, a precise and reliable connection can be achieved between the first transmission component 151 or the third transmission component 154 and the leading edge section 141, avoiding problems such as difficult assembly and weak connection caused by direct connection between the first transmission component 151 or the third transmission component 154 and the leading edge section 141. In addition, it facilitates the individual processing, assembly and subsequent maintenance of parts, reducing maintenance costs. Furthermore, the connector 16 can also buffer the vibration and impact during the transmission process, protecting the leading edge section 141 and the first transmission component 151 and the third transmission component 154, ensuring transmission accuracy.

[0067] In one embodiment, combined with Figure 2 and Figure 3 As shown, the connector 16 is inserted through the leading edge section 141 along the direction of the outer ring 13 toward the central guide member 12; one end of the connector 16 near the central guide member 12 is rotatably connected to the central guide member 12; one end of the connector 16 near the outer ring 13 passes through the outer ring 13 and is connected to the first transmission member 151 or the third transmission member 154.

[0068] In the view shown in the attached figure, the connector 16 is constructed as a columnar structure, such as a connecting shaft.

[0069] Thus, by having the connector 16 pass through the leading edge section 141 along the direction of the outer ring 13 toward the central guide member 12, and having its end near the outer ring 13 directly pass through the outer ring 13 to connect with the first transmission member 151 or the third transmission member 154, the installation position of the transmission member (first transmission member 151 / third transmission member 154) between the casing 11 and the outer ring 13 can form a precise radial alignment with the leading edge section 141, without the need for an additional adapter structure, which greatly reduces the difficulty of connecting and aligning the transmission member with the leading edge section 141. Meanwhile, one end of the connector 16 is rotatably connected to the central guide 12, which can stably position the connector 16 and prevent the connector 16 from shifting or misaligning during connection. This ensures that the transmission component and the leading edge section 141 are connected accurately and firmly. During assembly, the connector 16 and the leading edge section 141 can be assembled first, and then the transmission component can be connected, which simplifies the assembly process. During later disassembly and maintenance, the transmission component and the leading edge section 141 can also be easily separated, further improving the convenience of connection and maintenance.

[0070] In one embodiment, see [reference] Figure 3 As shown, the main body section 142 includes a middle section 142a and a tail section 142b. The middle section 142a is rotatably connected to the leading edge section 141. The side of the middle section 142a away from the leading edge section 141 is connected to the tail section 142b. A fuel passage is provided in the tail section 142b. A fuel nozzle is provided on the side wall of the tail section 142b. A flame stabilizing structure 142b1 is provided on the side of the tail section 142b away from the leading edge section 141.

[0071] From the perspective shown in the attached figure, the middle section 142a is constructed as an arc-shaped structure, and the central axis of the circle containing the arc-shaped structure is parallel to the central axis of the outer ring 13. The flame stabilizing structure 142b1 can be a V-shaped groove or a blunt body structure located on the side of the tail end away from the leading edge section 141 to form a low-speed recirculation zone. Fresh combustible mixture is continuously ignited in the low-speed recirculation zone to prevent the flame from being blown out by the high-speed airflow and to ensure that afterburner combustion can continue stably.

[0072] In one embodiment, the afterburner 10 further includes a controller (not shown) and a position sensor (not shown). The controller is connected to the position sensor and the drive mechanism 15. The position sensor is used to monitor the rotation angle of the leading edge section 141. The controller is used to control the operation of the drive mechanism 15 based on the rotation angle information monitored by the position sensor.

[0073] Thus, when the drive mechanism 15 drives the leading edge section 141 to rotate, the position sensor can monitor the rotation angle of the leading edge section 141 in real time and feed the angle information back to the controller to form a closed-loop control. The controller dynamically adjusts the operation of the drive mechanism 15 accordingly to ensure that the rotation angle of the leading edge section 141 is accurately adapted to the change of airflow direction, avoid the non-zero angle of attack caused by angle deviation, realize the automatic and precise adjustment of the angle of the leading edge section 141 without manual intervention, improve the adjustment efficiency and accuracy, and at the same time correct the angle deviation in time to ensure that the angles of all leading edge sections 141 are synchronized and consistent, further enhance the stability of the flow field, reduce the risk of airflow separation and oscillation, and adapt to the multi-condition operation requirements of the engine.

[0074] Secondly, see Figure 6 As shown, this application embodiment provides a control method for an afterburner 10 with adaptive adjustment of the leading edge of the support plate and the stabilizer. This method can be implemented using the afterburner 10 in the first aspect. The method includes:

[0075] S10, Obtain the airflow deflection angle β of the airflow entering the afterburner 10;

[0076] S20, based on the airflow deflection angle β and the installation angle θ of the support plate 14 fixed The target rotation angle δ of the leading edge segment 141 is calculated.

[0077] Specifically, the mounting angle θ of the support plate 14 fixed This refers to the installation angle of the middle section 142a of the support plate 14. The installation angle of the middle section 142a is 0 degrees, that is, the central axis of the circle containing the middle section 142a is parallel to the central axis of the outer ring 13.

[0078] S30. Control the leading edge segment 141 to rotate through the target rotation angle δ so that the tangent direction of the middle arc of the leading edge segment 141 is consistent with the airflow direction.

[0079] Specifically, the control drive mechanism 15 operates to drive the leading edge segment 141 to rotate relative to the main body segment 142, so that the leading edge segment 141 rotates through the target rotation angle δ, and the tangent direction of the middle arc of the leading edge segment 141 is consistent with the airflow direction.

[0080] The control method for adaptive adjustment of the support plate leading edge and stabilizer of the afterburner 10 provided in this application embodiment obtains the airflow deflection angle β of the airflow entering the afterburner 10, and determines the control method based on the airflow deflection angle β and the installation angle θ of the support plate 14. fixed The target rotation angle δ of the leading edge section 141 is calculated; then the leading edge section 141 is controlled to rotate through the target rotation angle δ so that the tangent direction of the mid-arc line of the leading edge section 141 is consistent with the airflow direction. In this way, the leading edge section 141 of the support plate 14 can adapt to changes in airflow direction, reducing the probability of the leading edge section 141 of the support plate 14 generating a non-zero angle of attack. This reduces the probability of airflow separation, flow field distortion and oscillation risk in the afterburner 10, maximizes the reduction of flow resistance loss, and improves thrust and combustion stability.

[0081] In one embodiment, in S10, obtaining the airflow deflection angle β of the airflow entering the afterburner 10 specifically includes:

[0082] Obtain the flow field parameters of the airflow entering the afterburner 10, or obtain the compressor speed and turbine pressure ratio;

[0083] Specifically, the flow field parameters of the airflow entering the afterburner 10 include the total pressure and static pressure at the inlet of the afterburner 10, which can be obtained by a pneumatic probe installed at the inlet of the afterburner 10. The compressor speed and turbine pressure ratio refer to the speed of the high-pressure compressor and the turbine pressure ratio of the engine.

[0084] The obtained flow field parameters, or the compressor speed and turbine pressure ratio, are input into the preset calibrated flow field model to calculate the airflow deflection angle β.

[0085] Specifically, the pre-defined process model can be established based on parameters such as engine speed, fuel flow rate, pressure, and temperature, combined with the engine's overall calculation formula and fluid dynamics simulation.

[0086] Thus, by obtaining the flow field parameters of the airflow entering the afterburner 10, or obtaining the compressor speed and turbine pressure ratio, and substituting these parameters into the preset calibrated flow field model, the airflow deflection angle can be obtained. This allows for the convenient calculation of the target rotation angle δ of the leading edge section 141, ensuring that the tangent direction of the mid-arc of the leading edge section 141 is consistent with the airflow direction. This enables the leading edge section 141 of the support plate 14 to adapt to changes in airflow direction, reducing the probability of the leading edge section 141 of the support plate 14 generating a non-zero angle of attack. Consequently, the probability of airflow separation, flow field distortion, and oscillation risks occurring in the afterburner 10 can be reduced, maximizing the reduction of flow resistance loss and improving thrust and combustion stability.

[0087] In one embodiment, in S20, the formula for calculating the target rotation angle δ of the leading edge segment 141 is:

[0088] δ=β-θ fixed .

[0089] The technical features of the above embodiments can be combined in any way. For the sake of brevity, not all possible combinations of the technical features in the above embodiments are described. However, as long as there is no contradiction in the combination of these technical features, they should be considered to be within the scope of this specification.

[0090] The embodiments described above are merely illustrative of several implementation methods of this application, and while the descriptions are relatively specific and detailed, they should not be construed as limiting the scope of the patent application. It should be noted that those skilled in the art can make various modifications and improvements without departing from the concept of this application, and these all fall within the protection scope of this application. Therefore, the protection scope of this patent application should be determined by the appended claims.

Claims

1. A booster combustion chamber with adaptive adjustment of the leading edge of the support plate and the stabilizer, characterized in that, It includes a casing, a central guide vane, an outer ring, and multiple support plates distributed circumferentially between the central guide vane and the outer ring; The support plate includes a leading edge section and a main body section distributed sequentially along the axial direction; the main body section connects the outer ring and the central guide member; the leading edge section is rotatably connected to the main body section. The afterburner also includes a drive mechanism connected to the leading edge section. The drive mechanism is used to drive the leading edge section to rotate relative to the main body section in order to adjust the angle of the leading edge section relative to the airflow direction.

2. The afterburner with adaptive adjustment of the leading edge of the support plate and the stabilizer according to claim 1, characterized in that, The drive mechanism is located between the outer ring and the housing, and the drive mechanism includes: A first transmission member is connected to the leading edge segment; A driving member is disposed on the outer ring or the housing; the driving member is connected to the first transmission member, and the driving member is used to drive the first transmission member to swing, so as to drive the leading edge segment to rotate relative to the main body segment.

3. The afterburner with adaptive adjustment of the leading edge of the support plate and the stabilizer according to claim 2, characterized in that, The drive mechanism further includes a second transmission component and multiple third transmission components; The second transmission member is disposed between the outer ring and the housing, and the second transmission member is constructed as a ring structure; the second transmission member is capable of rotating about the axial direction of the outer ring; The first transmission member is connected to the leading edge segment of one of the support plates; the end of the first transmission member away from the drive member is connected to the second transmission member via a spherical joint. The plurality of third transmission components are connected to the leading edge segments of the remaining support plates, and the plurality of third transmission components are all connected to the second transmission component through a spherical pair.

4. The afterburner with adaptive adjustment of the leading edge of the support plate and the stabilizer according to claim 3, characterized in that, The afterburner also includes a connector, which is connected to the leading edge section, and the first transmission member or the third transmission member is connected to the connector.

5. The afterburner with adaptive adjustment of the leading edge of the support plate and the stabilizer according to claim 4, characterized in that, The connector is inserted into the leading edge section along the direction from the outer ring toward the central guide member; The end of the connector near the central guide is rotatably connected to the central guide; the end of the connector near the outer ring passes through the outer ring and is connected to the first transmission member or the third transmission member.

6. The afterburner with adaptive adjustment of the leading edge of the support plate and the stabilizer according to claim 1, characterized in that, The main body section includes a middle section and a tail section. The middle section is rotatably connected to the leading edge section, and the side of the middle section away from the leading edge section is connected to the tail section. A fuel passage is provided in the tail section, a fuel nozzle is provided on the side wall of the tail section, and a flame stabilizing structure is provided on the side of the tail section away from the leading edge section.

7. The afterburner with adaptive adjustment of the leading edge of the support plate and the stabilizer according to claim 1, characterized in that, The afterburner also includes a controller and a position sensor. The controller is connected to the position sensor and the drive mechanism. The position sensor is used to monitor the rotation angle of the leading edge segment. The controller is used to control the operation of the drive mechanism based on the rotation angle information monitored by the position sensor.

8. A control method for an afterburner with adaptive adjustment of the leading edge of the support plate and the stabilizer, characterized in that, The method includes: Obtain the airflow deflection angle β of the airflow entering the afterburner; Based on the airflow deflection angle β and the mounting angle θ of the support plate fixed The target rotation angle δ of the leading edge segment is calculated. The leading edge segment is controlled to rotate through the target rotation angle δ so that the tangent direction of the mid-arc line of the leading edge segment is consistent with the airflow direction.

9. The control method for the adaptive adjustment of the leading edge of the support plate and the stabilizer in the afterburner according to claim 8, characterized in that, The step of obtaining the airflow deflection angle β of the airflow entering the afterburner includes: Obtain the flow field parameters of the airflow entering the afterburner, or obtain the compressor speed and turbine pressure ratio; The obtained flow field parameters, or the compressor speed and turbine pressure ratio, are input into the preset calibrated flow field model to calculate the airflow deflection angle β.

10. The control method for the adaptive adjustment of the leading edge of the support plate and the stabilizer of the afterburner according to claim 8, characterized in that, The formula for calculating the target rotation angle δ of the leading edge segment is: δ=β-θ fixed 。

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